Temporarily-installed aircraft observer door plug, chair, sonotube ejection and control system

ABSTRACT

In one embodiment, a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly are affixed to a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.13/738,935, filed on Jan. 10, 2013, which is a divisional of U.S.application Ser. No. 12/734,158, filed on Apr. 14, 2014, now U.S. Pat.No. 8,807,482, issued on Aug. 19, 2014, under 35 U.S.C. §371(c) as anational-stage entry of PCT/US08/11747, filed on Oct. 15, 2008, whichclaims priority to U.S. Provisional Application No. 60/998,959 filed onOct. 15, 2007, the entirety of which is hereby incorporated byreference.

TECHNICAL FIELD

This invention relates to a temporarily-mounted, portable, modular,aircraft-based scanner chair, bubble door plug, sonotube ejection andworkstation assemblies which do not require airframe modifications toaccommodate the temporary installation of the manned observation, storesjettisoning, and control systems.

BACKGROUND

Aircraft-based platforms are ideally suited for time sensitiveemergency, as well as routine, sensing, search, monitoring, surveillanceand response activities. Among the various types of equipment andmethodologies employed to maximize the effectiveness of aircraftemployed in these roles include the launch and telemetry control ofsonotube compliant stores which can include air launched MiniatureUnmanned Aerial Vehicles (MUAV's), smoke markers, illumination flares,communication radios, and Self Locating Data Marker Beacons (SLDMB's)common to those engaged in Search And Rescue operations (SAR). Otheraircraft enhancements in support of these missions can also includemanned observation systems which utilize specially positioned scanningchairs in conjunction with enlarged glazing surfaces typical of thoseused for SAR, aerial refueling, and missile scanning functions.

By way of example the Canadian Department Of Defense (DND) operatesLockheed Martin C-130 aircraft which are routinely engaged in SARoperations. DND achieves a limited capability to eject sonotubecompliant stores and to undertake manned observation from these aircraftby utilizing a pallet mounted, paratroop door located,temporarily-installed, chair and un-pressurized door plug which can beequipped with a hand launched sonotube port and large flush glazedwindow. Unfortunately, precision stores deployment, Global PositioningSystem (GPS) location, payload control, and data, audio, or videotelemetry from the stores is not possible without undertakingsubstantial modification to these aircraft. Further, DND cannot achieveHuman Factors Engineering (HFE) compliance with Military Standard 1472using the current palletized chairs or manned scanning techniquesemployed within the paratroop door plug flush mounted glazing systemrequires that the chair be positioned forward into the door plug for theSAR technician to achieve peripheral search maximization. Theanthropomorphic problems associated with this abnormal and at timesprolonged physical position when the observer cannot project his feetbeyond the curvature of the fuselage are numerous. By way of contrastthe United States Coast Guard (USCG) also uses the Lockheed Martin C-130for SAR missions. However, the USCG has undertaken substantial Group “A”or permanent modification of their aircraft rear ramps to achieveprecision sonotube delivery, telemetry, and control. The USCG alsoemploys a forward pressurized flat glazing observation system withdedicated sonotube launch system located at the observer chair positionsforward of the wings abreast both sides aft of the C-130 cockpitbulkhead. Although the USCG has achieved a degree of HFE compliance,again the chair positioning and flat glazing, limit the visual acuity ofthe observer.

Further, although competent companies like Benson Lund, of Essex,England have designed other observer chairs for stanchion posts, thechallenge of integrating a temporarily-installed chair with extensivemulti-axis HFE compliant positioning capabilities, which can fold awayout of the cargo space, and can be sufficiently restrained to theaircraft structure to meet crashworthy loading criteria, does notcurrently exist.

Further underscoring current deficiencies associated with the control ofjettisonable sonotube stores, new technologies exist which enable a hostaircraft to launch and receive video and data telemetry from smallMUAV's comparable to those manufactured by Advanced Ceramics Research,Inc. of Tucson, Ariz. USA, or as described in U.S. Pat. No. 6,056,237,entitled “Sonotube Compatible Unmanned Aerial Vehicle And System” issuedMay 2, 2000 to Richard L. K. Woodland, and incorporated herein byreference. The sonotube control interfaces currently employed on USCGaircraft and like C-130 aircraft do not permit the visual analysis oradvanced user interface and control of the deployed sonotube payloadsystems unless a palletized control system comparable to the PalletizedRadar Operating System (PROS) currently used by the USCG on their HC-130“Casper” aircraft can be employed wherein the air drop functions areagain compromised due to the co-location of the control system pallet inthe rear of the host aircraft cargo bay.

Similar deficiencies in other mission areas also exist wherein U.S. AirForce (USAF) Lockheed Martin MC-130's and U.S. Marine Corp (USMC) KC-130aircraft regularly engage in nighttime air to air helicopter refuelingoperations. These missions require that a loadmaster or other crewmember visually monitor the refueling operation from the paratroop doorlocation through a small flush window, often in turbulent flightconditions wearing NVG's on a simple fold away non-crashworthy seatwhich can be also attached to the door. Under these conditions aerialrefueling accidents have occurred resulting in lost and damagedaircraft.

Other situations involving hostile missile launch against large sloweraircraft comparable to the Boeing C-17 during the critical take-offphase have also resulted in lost and damaged aircraft. In order tocounter the vulnerability of aircraft to low altitude man portablemissile launch, the USAF air Mobility Command's (AMC) Battle Lab hasreleased a requirement for a manned bubble window observation system tosubstantially enhance the probability of undertaking successful evasivemaneuvers or timely activation of other counter measures.

Further, although several types of aircraft are currently operated withbubble windows and sonotube ejection systems, typically these systemsinvolve dedicated modifications that require a fleet of aircraft bemodified to maintain mission readiness. Hence in most cases becausethese manned observation and sonotube mission kits are costly to installand upgrade, they are usually undertaken in the context of “minimum butadequate” and suffer performance deficiencies in light of optimalcapabilities which could be achieved with fewer advanced technologiesthat are not permanently dedicated to one aircraft.

In pursuit of a prior solution, an aircraft door compatible mannedobservation and sonotube ejection system was described in U.S. Pat. No.5,927,648, entitled “aircraft Based Sensing, Detection, Targeting,Communications, and Response Apparatus” issued Jul. 27, 1999 to RichardL. K. Woodland, and incorporated herein by reference. Although theWoodland invention can be able to accommodate temporary mounting of thesystem described in U.S. Pat. No. 5,927,648 without incurring airframemodifications, it is completely reliant on a “mounting pallet” forinstallation which compromises all other backend air drop operationswhen the system is installed. Further, the Woodland patent does notaddress the temporary installation of an integrated door plug retractionsystem, multi-axis articulation of the observer chair, collapsibleworkstation, or unique form factor electronics and processing racksindependent of a pallet assembly.

Currently prior art, and practices associated with resolution of theaforementioned deficiencies are inadequate, costly, precludesimultaneous air drop operations, inhibit upgrade, increase theprobability of aircraft accidents during refueling operations and leavelarge slow moving cargo aircraft vulnerable to low altitude missilethreats. Accordingly there is an on-going, unaddressed need to achieve aflexible, rapidly installed, non-dedicated airborne manned observationand sonotube launch and control system mounting methodology for fixedand rotary wing cargo aircraft that does not interfere with air dropoperations, and does not require a pallet for installation.

SUMMARY

The apparatus and system of the present invention solves theaforementioned problems associated with temporarily-mounted, aircraftmanned observation and sonotube launch and control systems withoutcompromising air drop functionality by utilizing a variety of rapidlyinstalled adaptive mounting plates which interface with the hostaircraft's Air Deployment System (ADS) rails, the cargo floor tie downrings, seatbelt ring sockets and the emergency crew litter bar, therebyprecluding the requirement for a mounting pallet. The various mountingplate apparatus(s) can also be configured to match the cargo floor tiedown rings or tie down ring bolt socket patterns of a given hostaircraft in lieu of an ADS rail interface. In accord with the foregoing,one embodiment of the present invention integrates the simultaneousmounting, use, and stowage for in flight cargo aircraft operations of apressurized bubble door plug, a door plug retraction system, anarticulated multi-axis observer chair, a sonotube launch system, one ormore electronics LRU racks, a collapsible workstation, and a chairmounted collapsible remote operator control interface.

As the initial and primary component of the assembly summation, thebubble door plug of the present invention can be indented about itslower periphery to accommodate the simultaneous mounting and transitunder the door of a special mission strut and pod assembly describedunder a separate patent referenced herein as being simultaneously filedwith the U.S. Patent And Trademark Office (USPTO) by Neyedly andWoodland. When not using the strut assembly, the orifice created in thelower part of the pressurized door plug can be sealed with a close outpanel to permit aircraft pressurization. The door plug can also besegmented into two interlocking panels which permit modularity and rapidre-configuration of the respective panels in minutes. The HFE designeddoor assembly in either single or segmented configurations when using anobservation bubble incorporates a segmented two part window with abubble window in the upper section, a solid kick panel in the lower partof the bubble for the observers feet, and also accommodates theinstallation within the door plug of a heater/cooler unit manufacturedby Cox & Co. of New York, N.Y., USA, which provides temperaturecontrolled air to a diffuser located within the bubble window. A springloaded counterbalance door plug retraction system has also been devisedfor use with one embodiment of the current invention which can betemporarily-installed and used without removing the permanent aircraftdoor or retraction system. The door plug also accommodates thesimultaneous mounting of ballistic armor protection, a guided weaponinfra red/radar Electronic Warfare Self Protection (EWSP) system, astowable sonotube iris valve and launch tube, a black out curtain, anight vision goggle (NVG) compatible gooseneck light, a stowableobserver leaning bar, and an environmental/lighting control panel.

As an additional component comprising the assembly summation, a sonotubelaunch system can be attached to the door which incorporates an irisvalve which can be engaged or disengaged to permit launch of variouspayloads while the aircraft is in a pressurized or un-pressurizedcondition. The sonotube launch system incorporates a simple air bagexpansion technology housed within a small compressed air cartridgewhich was developed by Sea Corp, of Middletown, R.I., USA for the U.S.Navy LAMPS Helicopter. The Sea Corp mechanism eliminates the requirementfor large bulky sonotube pressurization systems or dangerous pyrotechnicdischarge devices which are currently used on U.S. Navy Lockheed MartinP-3's and other aircraft. The sonotube launcher can be also hinged andcan be stowed in flight on the side of the door or removed completelywhen not required or air drop activities are in progress.

One embodiment of the present invention further incorporates amulti-axis HFE designed stanchion post mounted observer chair asmanufactured by Benson Lund of Essex, England and AirDyne R & D ofCalgary Alberta, Canada, which can be stowed completely outboard of thecargo transit envelope in the rear of the aircraft, and deployed for usein several positions as may be required by the mission or aircraftoperational requirements. For example, for take-off and landing thechair can be positioned rearwards to comply with crashworthy 16 “G”requirements, or forward to use a workstation, or facing outboard forsearch operations, or 45 degrees aft or forward for aerial refueling andmissile scanning functions. The chair being HFE compliant alsoincorporates operator controlled vertical, horizontal, lumbar, andarmrest adjustment devices. Other attributes of the current chair of thepresent invention include ballistics armor, and the ability to mountremote sonotube or sensor system control interfaces on the armrestswithout permanently modifying the aircraft.

One embodiment of the present invention also incorporates simultaneousmounting and use of various mission electronics LRU rack assemblies, anda collapsible workstation with a collapsible remote chair mounted usercontrol interface. The workstation assembly can be mounted to the top ofa reduced height mission electronics LRU rack and can be furtherarticulated and divided into four modules which are hinged such that theworkstation can be disconnected for removal in whole or part, or canalso be stowed when not in use to permit air drop operations. Due tocrew survivability requirements and the possibility of mounting theworkstation assembly at varying locations within a host aircraft, theworkstation of one embodiment of the present invention also incorporatesa self contained recessed operator oxygen supply, mask, and controlsystem.

The integrated system of one embodiment of the present invention alsoincorporates connectivity to and utilization of, other ditching hatcheson the host aircraft which serve as temporary non-dedicated mountingsurfaces for Over The Horizon (OTH), or Line Of Sight (LOS) antennas insupport of communications, navigation, and positioning supportrequirements without sacrificing emergency crew egress or requirementfor interfacing with the mission LRU rack assemblies and the onboardaircraft electronic data bus. Further the complete system of the presentinvention may utilize various iron lung, medical litter, missile, winch,auxiliary or other existing electrical power interface receptacles todrive the various components and mission systems of the presentinvention on the host aircraft negating the requirement for dedicatedelectrical system modifications.

The simultaneous installation of the assembly as described hereincomprising one embodiment of the present invention can be removable,stowable, modular, rapidly installed, does not interfere with backendaircraft operations, does not compromise emergency crew egress, and doesnot require a pallet or aircraft modifications to enable its use on theground or in flight. The integration of the aforementioned componentsand assemblies in the non-dedicated manner embodied within the overallmanned observation and sonotube launch and control system describedherein, resolves the cited deficiencies to provide the desiredportability, commonality, and modularity to enable cost effectiveutilization of advanced technologies incorporated within the invention,across multiple aircraft types.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view of the complete assembly of all primarycomponents of the subject system apparatus depicted with a specialmission strut mounted beneath the pressurized two piece segmented andindented door plug with all components in the deployed and operableposition as could normally be installed on the left side of the hostaircraft.

FIG. 2 is a perspective view of the complete assembly of all primarycomponents of the subject system apparatus with attachment details, foran ADS rail equipped aircraft, depicted with all components in theretracted and stowed position utilizing a single piece indented doorplug with close out panel installed as depicted in the open position onthe left side of the host aircraft.

FIG. 3 is a perspective view of the complete assembly of all primarycomponents of the subject system apparatus with attachment details,depicted in the deployed and operable position as mounted to the cargofloor restraint rings of a host aircraft not equipped with ADS rails.

FIG. 4 is an exterior perspective view of a segmented, interlocking, twopiece pressurized observer door plug with an electronic warfare aircraftself protection system mounted in the lower door plug panel.

FIGS. 5A-5E are interior perspective views of the observer pivot armstanchion chair assembly depicting the adjustable motion paths about thesubject axis of the chair and stanchion post.

FIG. 6 is a perspective view of the workstation control assembly in thedeployed position depicting the oxygen supply reservoir, control system,and user mask.

FIG. 7 is a perspective view of the aft lower door plug retractionsystem attachment details more fully delineating the temporaryconnection methodologies employed.

FIG. 8 is a perspective view of the forward lower door plug retractionsystem attachment details more fully delineating the temporaryconnection methodologies employed.

FIG. 9 is a perspective view of the mission LRU rack attachment platemore fully delineating the temporary connection methodologies employed.

FIG. 10 is a perspective view of the temporary stanchion chairattachment plate more fully delineating the temporary connectionmethodologies employed.

DETAILED DESCRIPTION OF THE INVENTION

The invention is now described in terms of the FIGURES to more fullydelineate in detail the scope, materials, components, conditions, andmethods associated with the design, and deployment of the presentinvention. Many of the parts and components of the present invention arehereinafter described as being “assemblies”. As used herein, the word“assembly” or “assemblies” refers to the totality of related parts andpieces associated with a given component and its operability and is notto be construed as limiting to a particular piece, part, or operation.

The description herein is made with the understanding that the skilledperson in the field of designing and using aircraft-based platforms forsensing, search, monitoring, surveillance and response activities, isfamiliar with standard aircraft features such as various structuralelements including side doors, side door operations, floor tie downelements and systems, air deployment system (ADS) rails, and the like,primarily as utilized on C-130 aircraft. No detailed description of suchfeatures is believed necessary to enable one skilled in the art tounderstand and implement the present invention.

In general the invention comprises a novel design and integrationapproach to the configuration, capability, and installation of anaircraft independent, portable, manned observation and sonotube launchand control assembly as used in SAR, oil spill characterization, aerialrefueling, missile scanning, and other airborne missions.

A representative system architecture is depicted in FIGS. 1 through 3showing one embodiment of the present invention that can include an ADSrail, cargo floor mounted non-dedicated manned observation and sonotubelaunch and control system, and can include primary sub assemblies whichcan be used for functionality and employment of the present invention.Sub assemblies include an aircraft, mounting interface assembly, strutassembly, pressurized plug assembly, door plug retract assembly, and achair assembly, a workstation and control interface assembly. Combined,these various sub assemblies can enable a standard cargo aircraft to berapidly re-configured as a SAR mission platform, or alternatively, toenable an aircraft to be equipped with a rapidly installed advancedElectronic Warfare Self Protection (EWSP) system which could otherwisenot be installed due to the high cost of the systems or dedicatedairframe modifications.

As shown in FIGS. 1 and 2, the apparatus can be used aboard the hostaircraft 1, such as a Lockheed-Martin C-130 aircraft. The existingaircraft door 4 can be removed or opened vertically upward and stowed inthe locked position without being removed. The present inventionprovides the benefit of eliminating the need for palletized systems byincorporating mounting plates that attach to existing aircraft ADS railsand/or cargo tie down rings. As depicted in FIGS. 9 through 10,Installation of the illustrated embodiment of the present invention canbegin with attachment of an aft lower rail attachment fitting 83, whichis connected to the aft end of the ADS rail 12, using an adjustable CAMlock 18, as depicted in FIG. 7 and further a forward lower rail strutfitting 84, can be connected using multiple restraint bolt 21, meansfastened to the ADS rail 12, at which point an LRU rack mounting plate19, can be connected using a plurality of self tightening chock 23,means and a pair of restraint bolt 21, means, connected to several seatbelt socket 24 means, and the upper surface of the ADS rail 12, by meansof multiple adjustable CAM lock 18 means, and finally a stanchion postmounting plate 20, which is also mechanically connected to the uppersurface of the existing ADS rail 12, by means of adjustable CAM lock 18,means to multiple cargo tie down ring(s) 14. Attachment can be by use ofconventional aircraft adjustable cam locks 18, tension restraintdevices, or by other means familiar to those skilled in the art ofaircraft cargo restraint methodologies. If necessary, for example, wheninstalled on Lockheed-Martin C-130 aircraft, mounting plates such as theLRU rack mounting plate 19 can be further connected to the host aircraft1 by removing the temporary web seating bars and seat belt restraintring 15 and inserting multiple restraint bolts 21. The stanchion post99, can be connected to the side of the host Lockheed-Martin C-130aircraft 1 fuselage at its upper end by means of an upper stanchionbrace 102, which can be bolted to a fuselage structural flange 17 bymultiple restraint bolts 21.

Mounting plates can be made of any suitable material, such as aluminumor steel, depending on strength and weight constraints. Mounting placescan be made in any suitable shape, with the only design requirementbeing that they provide a surface for mounting the various components ofthe present invention and can be attachable to the aircraft's existingADS or cargo tie down rings.

After the various mounting plates and braces are installed, attachmentof a door plug retraction rail assembly 80, can be undertaken byconnecting upper rail support struts 81 to the existing aircraft doorretraction rail guides 6, by means of multiple upper rail attachmentfittings 82. The lower part of the temporarily-installed door plugretraction rail assembly 80 can be then connected to an existing ADSrail 12 by means of two lower rail attachment fittings 83 and multiplerestraint bolts 21. As depicted in FIGS. 1 through 3, the retractionrail assembly 80 may also be pre-assembled as a kit, and installed onthe host aircraft with either the one or two piece door plugs positionedwithin the retraction rail assembly 80.

As depicted in FIG. 3, where an aircraft is not equipped with an ADSrail 12, the present invention may utilized by installing one ormultiple adaptive floor plates 13 together with the use of restraintbolts 21 or conventional aircraft adjustable cam locks 18 for tensionrestraint. The adaptive floor plate 13 can include aircraft typespecific bolt patterns unique to the host aircraft, for example an EADSCN-235 aircraft.

After installation of the mounting plates and braces installation ofvarious functional mission assemblies may be undertaken using multiplesequential orders. Alternative functional mission assemblies can bepre-assembled as complete sub assemblies for rapid deployment. Examplesof sub assemblies which can be pre-assembled include the chair assemblywhich can be pre-assembled to the stanchion post 99, the upper stanchionbrace 102, and the stanchion post mounting plate 20.

As depicted in FIGS. 1 through 4 the current invention can include apressurized observer door plug assembly comprised of either a singlepiece door plug 51, or a segmented two piece door plug incorporating asegmented door plug upper panel 54, and a segmented door plug lowerpanel 55. In both configurations the pressurized observer door plugassembly utilizes a door strut indent 52, located along its lowerperiphery to accommodate the installation of a fixed or articulatedstrut 30 for special mission sensors antennas or other equipmentexterior of the aircraft. The pressurized observer door plug assemblyaccommodates the transit of the fixed or articulated strut 30 from theinterior side of the single piece door plug 51, or segmented door pluglower panel 55, to the exterior of the host aircraft while forming apressurized seal around the fixed or articulated strut 30. When thepressurized observer door plug assembly is used without the installationof a fixed or articulated strut 30, then a door plug close-out panel 53can be installed within the strut indent 52 to fill in the vacant areaand permit either aircraft to be pressurized. As depicted in FIG. 2,mechanical retention and securement of the door plug close-out panel 53can be achieved by a plurality of operator controlled close out panellatches 77, which can activate a plurality of close out panel lock pins78, which when extended in the single piece door plug 51, or thesegmented door plug lower panel 55, the door strut indent 52 becomeseffectively sealed to the outside air permitting the host aircraft to bepressurized.

As depicted in FIGS. 1 through 4, the pressurized observer door plugassembly 4.0, incorporates elements required for manned observationcommon to both the single piece door plug 51, and a segmented two piecedoor plug. These elements as installed within either the single piecedoor plug 51, or the segmented door plug upper panel 54, include asegmented bubble window 63, which incorporates clear glazing in theupper portion of the bubble and a metallic or composite door plug kickpanel 58 within the lower portion of the bubble assembly. The segmentedbubble window 63 assembly can also provide for a hinged door plugleaning bar 65 and a bubble window air diffuser 64, which can bemechanically ducted and electrically connected to a door plug heater/ACunit 60, and heater, diffuser, light control 61, unit mounted within theobserver door plug assembly. Either the single piece door plug 51 or thesegmented door plug upper panel 54 can provide for various door plugaccess panels 62 to gain entrance to the interior of the door formaintenance purposes and the mounting of a gooseneck or other type ofNVG compatible door plug light 59. The observer door plug assembly canbe powered by various means including a battery or 28 volt DC powercoming from the aircraft via a temporarily-installed cable harnessconnected to a floor winch, iron lung or other receptacle familiar tothose skilled in the art of aircraft electrical engineering.

As part of the mission hardware suite, and as depicted in FIGS. 1through 4, the observer door plug assembly can also incorporate asonotube launch system 67, comprised of a door plug tube port 66, whichprovides an orifice through either the single piece door plug 51, or thesegmented door plug upper panel 54, to enable ejection of sonotubecompliant stores. The door plug tube port 66 orifice can be connected toa sonotube iris valve 68 located on the inside of the host aircraftwhich can be manipulated between the open and closed positions to permitthe pressurized ejection of various sonotube compliant stores while theaircraft is pressurized. When not in use, or when required for air dropactivities, the sonotube launch system 67, can be equipped with asonotube hinge 69 and sonotube stowage latch 70 which permits theoperator to stow the sonotube launch system 67 along the upper sectionof either the single piece door plug 51, or the segmented door plugupper panel 54.

The single piece door plug 51 and the segmented door plug upper panel 54can also be equipped with door plug lift handles 57 and door plug lockpins 56, which effectively emulate the permanent aircraft door 4 lockmechanisms into the fuselage doorway. The two piece door plugconfiguration can also incorporate two or more interlocking latches 71which enable the segmented door plug lower panel 55 and segmented doorplug upper panel 54 to be joined for the purpose of sealing the door,pressurizing the aircraft, and allowing the segmented door plug lowerpanel 55 to be disengaged from the segmented door plug upper panel 54when a payload has been installed on the segmented door plug lower panel55. One embodiment of the present invention also incorporates themounting of a modified segmented door plug lower panel 55 equipped withan EWSP missile countermeasures fairing 74, which can be configured forinfra-red, radar, and/or RF countermeasure electronics.

As depicted in FIGS. 1 through 3 and FIG. 5 one embodiment of thepresent invention incorporates an observer chair assembly for thepurpose of engaging in manned search, missile scanning, aerial refuelingand other operations. The crashworthy observer chair 95 has beendesigned to articulate vertically about a stanchion post 99 by means ofa telescoping pivot arm 97 which can be attached to a stanchion posttranslation coupling 100 enabling rotation and elevation adjustmentabout the vertical axis of the stanchion post 99. The chair 95 can alsobe moved closer to or away from the stanchion post 99, in the horizontalaxis by means of a telescoping pivot arm sleeve 104, housed within theouter sleeve of the telescoping pivot arm 97. The observer chair 95,incorporates a translation control lever 98, which enables the chair,and thereby the system operator, to articulate 360 degrees about thevertical axis at the end of the telescoping pivot arm 97. Further, anadjustable slide plate 101 assembly allows the operator to adjust hisposition away from or closer to the vertical axis centerline at the endof the telescoping pivot arm 97, permitting the observer to move forwardinto the segmented bubble window 63. Several other aircraft interiormounting locations have been contemplated for the chair assembly, whichby way of example and not limitation could include mounting the chairassembly stanchion post 99 and stanchion post mounting plate 20 in ontoan aircraft floor 2, and to an alternate upper structural flange 17, ona lowered rear ramp of a Lockheed-Martin C-130 aircraft 1, for rearwardvision through the aft cargo area. Other features currently deemed ascommon practice within the aircraft military chair industry could alsoprovide for the integration of armor, foot rests, heating pads, andother components related to crew comfort and survivability.

As depicted in FIGS. 1 through 3 and FIG. 6 a workstation & controlinterface assembly can be incorporated within the current invention forthe purpose of launching/controlling various sonotube based payloads,undertaking mission specific data processing, communications, EWSPactivities and other unique mission systems control functions. Thehardware suite required to undertake the control interface functionalityand permit stowage outboard of the host aircraft ADS rail 12 can includea collapsible workstation 112, one or more remotely located collapsiblearmrest mounted control interfaces 121, and at least one or more missionelectronics LRU racks 111 housed within a crashworthy cabinet frame.

One embodiment of the present invention as disclosed in FIGS. 1 and 6,include a form fitted reduced height LRU rack 125 and a full heightmission electronics LRU rack 111, both of which can be contoured tocomply with the fuselage curvature typical of the host aircraft. Forexample, on a Lockheed-Martin C-130 aircraft 1, the components can becontoured so as to accommodate fitment outboard of the ADS rail 12, andcargo transit envelope where a removable web bench seat could normallybe located. The reduced height LRU rack 125, and mission electronics LRUrack 111, can be connected to the LRU rack mounting plate 19 by aplurality of restraint bolts 21 and when required, stabilized verticallyby a plurality of attachment clamps 22, temporarily-affixed to the hostaircraft litter bar 16. The reduced height LRU rack 125 and missionelectronics LRU rack 111 generally occupy two mounting positionsapproximately consistent with the 21 inch electronics LRU mounting rackstandard. The LRU rack positions can be able to accommodate either twofull height mission electronics LRU racks 111, or one collapsibleworkstation 112 mounted to the upper surface of a reduced height LRUrack 125.

One embodiment of the current invention also accommodates the temporarymounting and utilization of the collapsible workstation 112, consistingof an upper display module 113, a lower display module 114, a tactileinterface module 115, and an overhead module 116, The modules beingphysically connected and appropriately hinged so as to enable collapseand stowage using a plurality of module locking hinges 117. All modulesincorporated within the collapsible workstation 112 can be equipped withself-locking deployed/stowed hinge devices using operator induced modulehinge release actuators 118 and other slide rail devices and hingescommon to those skilled in the field of flight mechanics, to enablecollapse and stowage of the collapsible workstation 112 outboard of theaircraft cargo transit envelope as to permit air drop activities. Thecollapsible workstation 112, accommodates common control, display, soundand input devices such as a joystick 129, keyboard, track ball, pointingstylus, audio speakers, and display screens. The joystick 129, isdescribed herein as being removable to enable stowage underneath eitherthe left or right side hinged wrist pad 126 within a wrist pad bin 127.To compensate for turbulence induced injuries, and fatigue exerted onthe operator, the forward edges of the tactile interface module 115, andthe overhead module 116, can be equipped with a chamfered foam edging128 to provide a soft anthropomorphic interface between the operator andthe solid frame of the collapsible workstation 112.

Further as depicted In FIG. 6, as several aircraft types do not have asupplementary oxygen supply, mask, and control system for specialmission crew members, the collapsible workstation 112 can incorporatethe integration of a self contained oxygen cylinder means housed withinthe frame of the tactile interface module 115, accessible from a panelbelow, and a set of oxygen controls 124 housed underneath the left orright side hinged wrist pad 126, within a wrist pad bin 127, and anoxygen mask 122 housed within a rapid access bin on the underside of thetactile interface module 115. The oxygen systems can be typical of theMA-1 assembly manufactured by Scott Aviation of Lancaster, N.Y., USA.

Further as depicted In FIGS. 1 through 3, due to the fact that thecollapsible workstation 112 system operator may rotate his chairposition between the collapsible workstation 112 and the side lookingobserver position located in the aircraft doorway, or because flightcrew members located in the cockpit, or at other locations on the hostaircraft may require remote control interface means and remoteelectronic connectivity to the workstation & control assembly, thepresent invention incorporates the integration of one or morecollapsible armrest mounted control interfaces 121 connected to thecollapsible workstation 112 by data/power cabling familiar to thoseskilled in the art of aircraft electrical engineering.

In one embodiment of the current invention as it relates to theworkstation & control assembly, the invention components can also beelectronically interfaced to the aircraft data bus or connected to amodified temporarily-mounted, ditching hatch plug 72 (as shown in FIG.1), equipped with various types of hatch mounted RF antennas 73 and GPSantennas 75 located topside on the fuselage for mission specific line ofsight (LOS) and satellite based over the horizon (OTH) communicationsand telemetry without permanent modification to the host aircraft. Themodified ditching hatches are of the type routinely employed on USAFC-130 aircraft and typical of those manufactured by AerospaceIntegration Corp, of Crestview, Fla., USA.

Method of Operation

The method of operation is described in conjunction with FIGS. 1 through6 and includes methodologies generally known in the art of cargorestraint methodologies, sonotube ejection systems, manned observationsystems, communications, telemetry and control of the sonotube compliantpayloads. Therefore, details known to those skilled in the art ofaircraft cargo restraint, aircraft payload loading, restraining, anduse, are not described in exhaustive detail herein.

In general, the mounting plates of the present invention can be mountedfirst on their respective components, or they can be mounted first onthe aircraft, such as on the aircraft's ADS rail. In the methodologydescribed herein, the various mounting plates are considered to havebeen already attached to their respective mission components. Themethodology of installation and operation as described herein is dividedinto seven functional areas. The installation of a temporarily-mountedfixed or articulated strut 30, although referenced briefly herein, isnot described further with regard to operation as it is described indetail in a parallel patent filed by Woodland & Neyedly with the U.S.Patent & Trademark Office (USPTO) as part of a family of related specialmission inventions undergoing simultaneous filing. Further, although thepresent invention can be utilized on various types of aircraft, themethodology below is described with respect to a rear-loading C-130 typeaircraft.

System Transport & Loading—Upon notification of a mission, a ground crewthat can be comprised of two individuals could ship the presentinvention within a plurality of man portable, ruggedized transport casesto the host aircraft. After an initial confirmation that the hostaircraft is flight ready, the rear ramp could be lowered and thetransport cases loaded onto the aircraft. In one embodiment of theinvention, the loading can be achieved without the use of a mechanizedloader, the components and assemblies being light enough that twoindividuals can undertake the loading and installation.

Aircraft Preparation—Initially the install crew could open, stow, orremove one or more side door(s), such as a left side paratrooper door,to create an orifice with which to accommodate fitment of thepressurized observer door plug assembly. One or more of the upward hostaircraft ditching hatches 5, could also be removed to accommodate one ormore specialized ditching hatch plugs 72 to provide specialized missiontelemetry, and communications capabilities. Once the host aircraftditching hatch 5 has been removed, the web seating bench located forwardof the paratroop door(s) can be removed and stowed. If a fixed orarticulated strut 30 is used with the present invention then a sectionof the existing ADS rail 12 could also be removed to accommodate itsinstallation abreast of the open doorway.

Workstation And Control Interface Assembly—The installation of thevarious electronics and user interface assemblies of the presentinvention begins with the mission electronics LRU rack 111, and reducedheight LRU rack 125, wherein as stated in the operational description,these components can be pre-connected to the LRU rack mounting plate 19,which in turn is temporarily-attached to the host aircraft floor 2, andhost aircraft fuselage 3, by means of an ADS rail 12, or an adaptivefloor plate 13. The fastening methodologies used as described herein caninclude a plurality of aircraft cargo tie down rings 14 and removal ofthe seat belt restraint rings 15, a litter bar 16, using a plurality ofrestraint bolts 21 and attachment clamps 22. Once the reduced height LRUrack 125 is installed together with a collapsible workstation 112, theinstallation crew could attach it to the top of the reduced height LRUrack 125, using a plurality of collapsible workstation slide rails 130.The installation crew could then extend the collapsible workstation 112by releasing a plurality of module locking hinges 117 by depressingmultiple module hinge release actuators 118. Once fully extended andsecured to the top of the reduced height LRU rack 125, one crew membercould lift the hinged wrist pad 126, and remove the joystick 129, fromwrist pad bin 127, to insert in either a left or right hand joysticksocket 131, located on the tactile interface module 115. At this pointin the installation process, the collapsible workstation 112, missionelectronics LRU rack 111, reduced height LRU rack 125, and the ditchinghatch plug 72, can be inter-connected by a power and data relay/controlcable and approved electrical power from the host aircraft usingmaterials and methods familiar to those skilled in the art of aircraftelectrical engineering.

Observer Chair Assembly—The observer chair 95, equipped with a pair ofchair armrests 96, a translation control lever 98, and an adjustableslide plate 101, could be pre-assembled with the stanchion post 99,integrating in one assembly the stanchion post translation coupling 100,telescoping pivot arm 97, and upper stanchion brace 102, with theobserver chair 95. The size and weight of this assembly can be quitemanageable by two crew members who can connect the stanchion postmounting plate 20 to the host aircraft floor 2, using adjustable camlock 18, means interfaces to a plurality of cargo tie down ring 14,means mounted on the surface of an ADS rail 12, or an adaptive floorplate 13. The stanchion post 99 also can be secured at the upper end tothe host aircraft fuselage 3 by an upper stanchion brace 102 and aplurality of restraint bolts 21, which can be connected to a structuralflange 17 on the host aircraft. Once the observer chair 95 is installedthe crew can mount the collapsible armrest mounted control interface121, and the chair armrest 96, and connect them to the collapsibleworkstation 112 by means of a power and data cable harness. Depending onthe nature of the mission(s) and the requirement for user interfaces,the collapsible armrest mounted control interface 121 may be positionedsimultaneously at multiple locations in the aircraft necessitating avariety of temporarily-installed cable harness configurations familiarto those skilled in the art of aircraft electrical engineering.

Pressurized Observer Door Plug Assembly—Installation of the temporaryobserver door plug and retraction rail assembly 80 for the purposes ofthis description of methodology assumes that either of the single piecedoor plug 51 or the two piece door plug comprised of a segmented doorplug upper panel 54 and a segmented door plug lower panel 55 ispre-assembled with the retraction rail assembly 80, and does not requireplacement of a door plug close-out panel 53, or operation of the doorplug lock pins 56. In one embodiment of the present invention, thedesign addresses the installation of the complete door plug assembly bytwo individuals by aligning the upper rail support struts 81, of theretraction rail assembly 80, with the existing aircraft door retractionrail guides 6, and secures a plurality of upper rail attachment fitting82 using restraint bolts 21 or other attachment clamps 22, or rotatingcam means familiar to those skilled in the art of aircraft mechanicalsystems engineering. The lower parts of the retraction rail assembly 80are connected to the to the host aircraft floor 2 using a pair of foreand aft lower rail attachment fittings 83, which can interface to thedoor retract mounting plate(s) 11, and are secured by several adjustablecam locks 18, and/or restraint bolts 21 interfaced to a plurality ofcargo tie down rings 14 mounted on the surface of an ADS rail 12 or anadaptive floor plate 13. Once the pressurized observer door plugassembly has been installed, the sonotube launch system 67 can beremoved from its case and attached to the sonotube iris valve 68 mountedwithin either the single piece door plug 51 or segmented door plug upperpanel 54. The tube comprising the majority of the sonotube launch system67 can be physically attached to the sonotube iris valve 68 using aplurality of bayonet latches which secure the tube in place once it hasbeen inserted into the bayonet recesses and rotated, which locks thesonotube launch system 67 in place.

System Functionality Check—The installation completed, the crew couldthen undertake a self diagnostics status verification test of thecollapsible workstation 112 and the onboard LRU processing system. Thiscould include all displays, input and output devices, cable connectionsto the hatch mounted RF Antenna 73, GPS Antenna 75, EWSP MissileCountermeasures Fairing 74, telemetric links to the payload stores ofthe sonotube launch system 67, one or more the collapsible armrestmounted control interface 121, and the aircraft data bus (if required).Additional status verification could include physical inspection andoperability of the self contained oxygen system within the collapsibleworkstation 112 by lifting the hinged wrist pad 126, to expose theoxygen controls 124, and removing the oxygen Mask 122, to verify theoxygen cylinder 123, was providing the requisite oxygen at the specifiedflow rates. Additional functional testing could be undertaken to assessoperability of the door plug Retract assembly 5.0, to verify pressurizedclosure of the fuselage door plug lock pins 56, the segmented door pluginterlocking latches 71, and the heater, diffuser, light control 61,could also be tested for operability and secure detent positioning. Thedoor mounted sonotube launch system 67, could also be checked for ratedpressurization of the launch cylinders, clearances of FOD from door plugtube port 66, operability of the sonotube iris valve 68, and operabilityof the sonotube hinge 69, and sonotube stowage latch 70, assemblies. Thefunctionality of the observer chair 95, in all its operable axis andadjustment modes is also undertaken and the telescoping pivot arm 97,extended to the bubble window observation position, A final inspectionof all system electrical cable harnesses, and structural interfaceattachment points which have been fitted with temporary restraint bolt21, means, attachment clamps 22, and adjustable cam lock 18, can beundertaken prior to approval for flight.

In Flight Operation—With the system of the present invention in thedeployed position aboard the host aircraft, the crew can engage inmanned search or scanning operations. As depicted In FIGS. 5A, 5B, 5C,5D, 5E, and 5F, the observer chair 95 can be rotated about the stanchionpost 99 to move back and forth between the collapsible workstation 112,and the segmented bubble window 63. The operator is also able to rotatehis chair through 360 degrees about the end of the telescoping pivot arm97 to achieve various viewing positions including positions advantageousfor take-off or landing, lateral mission scanning, or 45 degrees ineither forward or aft positions. Further, depending on height adjustmentthe chair can be elevated in the vertical about the stanchion post 99 bymeans of the stanchion post translation coupling 100. When viewingsubjects of opportunity from the segmented bubble window 63 the operatorcan adjust the chair forward and back into the window envelope using anadjustable slide plate 101 and translation control lever 98. Alladjustments and articulations can be achieved by known means as known inthe art.

As depicted in FIG. 2, when the chair is not required, or when back endair drop missions are being undertaken, the observer chair 95,collapsible workstation 112, and sonotube launch system 67 can be foldedaway outboard of the ADS rail 12 or cargo envelope to allow pallets andother cargo to egress towards the rear of the aircraft. When the hostaircraft is engaged in paratroop drop operations through the door whichthe present invention is mounted in, then the pressurized observer doorplug assembly lock mechanisms can be disengaged by the door lock handle76 located towards the upper left of the door assembly, which can beopened upward as it could normally operate to allow the paratroopers toegress without being constrained by the various components andappendages of the present apparatus.

When utilizing the sonotube launch system 67, images from variousjettisoned sonotube compatible payloads can be received by the hostaircraft. With the workstation & control assembly installed, dynamicallylaunched MUAV's can be tasked, and data analyzed by the host aircraftand then relayed to other aircraft, surface assets, or to distantcontrol centers using OTH telemetry provided by the specially equippedditching hatch plug 72. Further, when deploying multiple sonotube buoysor like packages the ditching hatch plug 72, provides GPS location datasuch that a grid of coordinated positions can be determined forprecision delivery of the sonotube packages, particularly if sonotubelaunch system 67, is equipped with multiple launch tubes, orincorporates a cartridge system similar that being developed by Sea Corpof Rhode Island, USA.

It could be obvious to those skilled in the art of aircraft specialmission systems that the overall system of the present invention asdescribed herein has extensive ability to interface with and otherwiseaccommodate numerous other missions when augmented with externalsensors, communications, electronic warfare systems, unmanned vehiclesor other stores, not described in detail within this patent. Whilecertain embodiments have been shown and described, various substitutionsand modifications may be made without departing from the spirit andscope of the invention. Accordingly it is to be understood that thepresent invention has been described by way of illustration and notlimitation.

What is claimed:
 1. A method of installing a temporarily-mounted controlsystem on an aircraft comprising: removing a door of the aircraft,wherein removal of the door creates an opening in the fuselage of theaircraft; attaching one or more workstation assemblies to the aircraft,wherein the attaching comprises: mounting the workstation assemblies onone or more line-replaceable unit (LRU) racks; and connecting the one ormore LRU racks to one or more mounting plates, wherein the mountingplates are connected to one or more adaptive floor plates, each adaptivefloor plate being connected to a floor of the aircraft; attaching anobserver chair assembly to the floor of the aircraft, wherein theobserver chair assembly is further connected to the one or moreworkstation assemblies; and attaching a temporary door plug and aretraction rail assembly to the aircraft, wherein: the temporary doorplug is adapted to fit the opening in the fuselage of the aircraft; thetemporary door plug is attached to the retraction rail assembly; and theretraction rail assembly is connected to the fuselage of the aircraft.2. The method of claim 1, wherein the one or more of the LRU racks arecontoured, wherein the contour complies with a fuselage curvature of theaircraft.
 3. The method of claim 1, wherein the mounting plates arefurther operable to connect the one or more LRU racks to the floor ofthe aircraft via an upper surface of an Air Deployment System (ADS) railconnected to the floor of the aircraft.
 4. The method of claim 1,wherein removing the door of the aircraft comprises opening the doorvertically and stowing the door in a locked position.
 5. The method ofclaim 1, wherein the workstation assemblies comprise a plurality ofphysically connected modules, wherein the physically connected modulescomprise one or more of: an overhead module; an upper display module; alower display module; or a tactile interface module.
 6. The method ofclaim 5, wherein two or more of the physically connected modules arephysically connected at least by one or more locking hinges.
 7. Themethod of claim 1, wherein at least one of the one or more workstationassemblies is further electronically interfaced to one or more of: adata bus of the aircraft; or a modified ditching hatch plug.
 8. Themethod of claim 1, wherein the connecting the observer chair assembly tothe one or more workstation assemblies comprises a connection betweenthe one or more workstation assemblies and a control interface of theobserver chair assembly, wherein the connection comprises at least powerand data cables.
 9. The method of claim 1, wherein the temporary doorplug comprises a segmented two-piece observation bubble comprising aprotruding upper segment portion and a protruding lower segment portion,wherein: the upper segment portion comprises a transparent glazing; thelower segment portion comprises a composite or metal protruding kickpanel; and the segmented two-piece observation bubble is continuous inshape from the upper segment portion through the lower segment portion.10. The method of claim 9, wherein the temporary door plug furthercomprises: a door plug upper panel comprising the segmented two-pieceobservation bubble; and a door plug lower panel.
 11. The method of claim1, wherein the temporary door plug further comprises one or more upperrail support struts operable to interface with the retraction railassembly.
 12. The method of claim 1, wherein the temporary door plugcomprises: a door plug upper panel; and a door plug lower panel which iscontoured and indented about its lower proximity to accommodate apressurized seal around the periphery of an articulated- orfixed-position payload strut which transits from the interior to theexterior of the aircraft.
 13. The method of claim 12, wherein the doorplug upper panel further comprises: a tube port that provides an orificethrough the door plug upper panel; and a valve interfaced with the tubeport that is operable between an open position and a closed position.14. The method of claim 12, wherein the temporary door plug furthercomprises two or more interlocking latches that are operable to: jointhe door plug lower panel and the door plug upper panel; and disengagethe door plug lower panel from the door plug upper panel.
 15. The methodof claim 1, wherein connecting the retraction rail assembly to thefuselage of the aircraft comprises: aligning an upper portion of theretraction rail assembly with a retraction rail guide of the aircraft;and connecting a lower portion of the retraction rail assembly to thefloor of the aircraft using fore and aft lower rail attachment fittingsoperable to interface to a door retract mounting plate of the aircraft.16. The method of claim 1, wherein the attaching the observer chairassembly to the floor of the aircraft comprises: attaching a stanchionpost mounting plate to the floor of the aircraft; and attaching astanchion post of the observer chair assembly to the stanchion postmounting plate.
 17. The method of claim 16, wherein the stanchion postis further connected to the fuselage of the aircraft using an upperstanchion brace and a plurality of restraint bolts.
 18. The method ofclaim 16, wherein the observer chair assembly further comprises: atelescoping pivot arm operable to interface with the stanchion post; andan observer chair operable to interface with the telescoping pivot arm.19. A method of installing a sonotube launch system in atemporarily-mounted door plug assembly of an aircraft comprising:attaching a temporary door plug and a retraction rail assembly to anopening in the fuselage of the aircraft, wherein the temporary door plugcomprises: a tube port that provides an orifice through the temporarydoor plug; and a sonotube iris valve connected to the tube port on aninterior side of the temporary door plug, wherein the sonotube irisvalve is operable between an open position and a closed position; andmounting the sonotube launch system on the temporary door plug, wherein:the sonotube launch system comprises a tube; and mounting the sonotubelaunch system comprises attaching the tube of the sonotube launch systemto the sonotube iris valve via a plurality of bayonet latches.
 20. Atemporarily-mounted control system for an aircraft comprising: atemporary door plug assembly, wherein: the temporary door plug assemblyis configured to fit in an opening in a fuselage of the aircraft, theopening being created by removal of a door of the aircraft; and thetemporary door plug assembly is connected to the aircraft using one ormore retraction rail assemblies; a workstation assembly, wherein: theworkstation is mounted on a line-replaceable unit (LRU) rack, whereinthe LRU rack is temporarily connected to a floor of the aircraft usingone or more mounting plates, wherein the mounting plates are connectedto: one or more adaptive floor plates, each adaptive floor plate beingconnected to a floor of the aircraft; or one or more Air DeploymentSystem (ADS) rails of the aircraft; and an observer chair assemblycomprising an observer chair mounted on a stanchion post connected tothe floor of the aircraft, wherein: the observer chair assembly isconnected to the workstation assembly via a power and data cableharness; and the stanchion post allows the observer chair to be rotatedto face either the workstation assembly or the temporary door plugassembly.